CN106089445A - The bullet electromotor that a kind of high-altitude ignition starts - Google Patents
The bullet electromotor that a kind of high-altitude ignition starts Download PDFInfo
- Publication number
- CN106089445A CN106089445A CN201610607726.0A CN201610607726A CN106089445A CN 106089445 A CN106089445 A CN 106089445A CN 201610607726 A CN201610607726 A CN 201610607726A CN 106089445 A CN106089445 A CN 106089445A
- Authority
- CN
- China
- Prior art keywords
- electromotor
- bullet
- submerged inlet
- blanking cover
- altitude
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The present invention relates to the bullet electromotor that a kind of high-altitude ignition starts, the bullet aeroturbine jet and the turbofan high-altitude ignition that solve current equipped Submerged Inlet start difficult problem, it is internal that the bullet electromotor that described high-altitude ignition starts is installed on aircraft (1), including: electromotor (6) and Submerged Inlet (3), described electromotor (6) is connected by ring flange (4) with described Submerged Inlet (3), the described rubber seal (5) in ring flange (4) groove, described Submerged Inlet (3) import department is provided with front blanking cover (2), electromotor (6) nozzle is provided with rear blanking cover (8)；Described electromotor (6) is internal equipped with starting motor (7), after aircraft (1) general assembly completes, and evacuation internal to electromotor (6) and Submerged Inlet (3).
Description
Technical field
The present invention relates to a kind of bullet electromotor, the bullet electromotor that a kind of high-altitude ignition starts.
Background technology
Starting to tackle electromotor in-flight ingition, traditional mode is to use pyrotechnic initiator and pyrotechnic igniter, electricity
The mode that lighter combines starts, and Submerged Inlet is often selected as the air intake installation of electromotor.
But, electromotor must solve in high-altitude (such as 7000m) this key technology of ignition start, embedded type air inlet
The road low total pressure recovery coefficient under engine ignition start-up period low discharge state makes this difficult problem of high-altitude ignition become more
High challenge.Main difficulty is that pyrotechnic initiator is difficult to electromotor band is gone to 65.0% under conditions of electromotor is full of air
The above rotating speed of slow train, after pyrotechnic initiator end-of-job, turbine still can not provide enough merits to maintain compressor to air-flow
Carry out supercharging.
Summary of the invention
The purpose of the present invention: in order to solve currently to be equipped with the bullet aeroturbine jet of Submerged Inlet and turbofan
Electromotor high-altitude ignition starts difficult problem, and the present invention proposes the bullet electromotor that a kind of high-altitude ignition starts.
Technical scheme:
The bullet electromotor that a kind of high-altitude ignition starts, the bullet electromotor that described high-altitude ignition starts is installed on flight
Device (1) is internal, including:
Electromotor (6) and Submerged Inlet (3), described electromotor (6) and described Submerged Inlet (3) pass through flange
Dish (4) connects, and the described rubber seal (5) in ring flange (4) groove, described Submerged Inlet (3) import department is provided with
Front blanking cover (2), electromotor (6) nozzle is provided with rear blanking cover (8)；Described electromotor (6) is internal equipped with starting motor (7), flies
After row device (1) general assembly completes, evacuation internal to electromotor (6) and Submerged Inlet (3)；
When described electromotor (6) prepares ignition start, under vacuum, described starting motor (7) is used to incite somebody to action
The direct band of electromotor (6) rotating speed goes to more than 90% rotating speed；Then open described front blanking cover (2) and rear blanking cover (8), and allow
The pyrotechnic initiator of electromotor (6) starts working to maintain electromotor (6) rotating speed, opens pyrotechnic igniter and electric ignition simultaneously
Device, it is achieved the ignition start in more than the 7000m high-altitude of electromotor (6).
Advantages of the present invention: what the present invention proposed utilizes evacuation to realize the bullet electromotor that high-altitude ignition starts, is passing
On the basis of system start mode, set with the Seal Design of engine air circulation road and engine embedded starting motor by air intake duct
Meter, is gone to more than 90% relative rotation speed by starting motor by engine speed band under vacuum conditions, then uses pyrotechnics trigger
Maintain high rotating speed and start combustion chamber ignition starting electromotor.The present invention can be electromotor rising in broad envelope
Move and provide reliable guarantee, solve the difficult problem that high-altitude ignition starts, there is significant engineer applied and be worth.
Accompanying drawing illustrates:
Fig. 1 be a kind of high-altitude ignition of the present invention start bullet engine assembly on board the aircraft overall structure signal
Figure.
Fig. 2 is the overall structure schematic diagram of the bullet electromotor that a kind of high-altitude ignition of the present invention starts.
Fig. 3 is the partial structurtes schematic diagram of the bullet electromotor that a kind of high-altitude ignition of the present invention starts.
Detailed description of the invention:
Below in conjunction with the accompanying drawings the present invention is described in further detail.
As Figure 1-3, the bullet electromotor that a kind of high-altitude ignition starts, the bullet that described high-altitude ignition starts is with starting
It is internal that machine is installed on aircraft 1, including:
Electromotor 6 and Submerged Inlet 3, described electromotor 6 is connected by ring flange 4 with described Submerged Inlet 3,
The described rubber seal 5 in ring flange 4 groove, described Submerged Inlet 3 import department is provided with front blanking cover 2, and electromotor 6 sprays
Rear blanking cover 8 it is provided with at Kou；Described electromotor 6 is internal equipped with starting motor 7, after aircraft 1 general assembly completes, to electromotor 6
Evacuation internal with Submerged Inlet 3；
When described electromotor 6 prepares ignition start, under vacuum, described starting motor 7 is used to start
The direct band of machine 6 rotating speed goes to more than 90% rotating speed；Then open described front blanking cover 2 and rear blanking cover 8, and allow electromotor 6
Pyrotechnic initiator starts working to maintain electromotor 6 rotating speed, opens pyrotechnic igniter and electric igniter, it is achieved electromotor 6 simultaneously
The ignition start in more than 7000m high-altitude.
Operation principle:
The premise of evacuation is to ensure that the sealing of electromotor.Because electromotor is connected with Submerged Inlet, according to flying
The Normal practice of row device, installs blanking cover in Submerged Inlet entrance location and provides the sealing of import, at air intake duct and electromotor
Junction uses ring flange, sealing ring and glue to provide and seals, and also uses blanking cover to provide at engine nozzle and seal.Ensureing
On the premise of electromotor seals, then carry out evacuation process to from the whole gas channel of Fighter Inlet to engine nozzle.
After electromotor reaches vacuum state, before blanking cover igniting is put in formal throwing, use built-in galvanic electricity of electromotor
Machine forwards engine speed band to 90% relative rotation speed more than easily, then opens blanking cover, fuel oil electric detonation valve, oxygen cylinder,
Refire pyrotechnic initiator, finally open pyrotechnic igniter and electric igniter completes electromotor and starts.
Claims (1)
1. the bullet electromotor that a high-altitude ignition starts, it is characterised in that the bullet electromotor that described high-altitude ignition starts
It is installed on aircraft (1) internal, including:
Electromotor (6) and Submerged Inlet (3), described electromotor (6) and described Submerged Inlet (3) pass through ring flange
(4) connecting, the described rubber seal (5) in ring flange (4) groove, before described Submerged Inlet (3) import department is provided with
Blanking cover (2), electromotor (6) nozzle is provided with rear blanking cover (8)；Described electromotor (6) is internal equipped with starting motor (7), flight
After device (1) general assembly completes, evacuation internal to electromotor (6) and Submerged Inlet (3)；
When described electromotor (6) prepares ignition start, under vacuum, described starting motor (7) is used to start
The direct band of machine (6) rotating speed goes to more than 90% rotating speed；Then open described front blanking cover (2) and rear blanking cover (8), and allow and start
The pyrotechnic initiator of machine (6) starts working to maintain electromotor (6) rotating speed, opens pyrotechnic igniter and electric igniter simultaneously, real
The ignition start in more than the 7000m high-altitude of existing electromotor (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610607726.0A CN106089445B (en) | 2016-07-29 | 2016-07-29 | The bullet engine that a kind of high-altitude ignition starts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610607726.0A CN106089445B (en) | 2016-07-29 | 2016-07-29 | The bullet engine that a kind of high-altitude ignition starts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106089445A true CN106089445A (en) | 2016-11-09 |
| CN106089445B CN106089445B (en) | 2018-05-04 |
Family
ID=57479112
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610607726.0A Active CN106089445B (en) | 2016-07-29 | 2016-07-29 | The bullet engine that a kind of high-altitude ignition starts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106089445B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN114062816A (en) * | 2021-11-17 | 2022-02-18 | 四川航天长征装备制造有限公司 | Electric explosion valve test system and test method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2045430U (en) * | 1988-11-15 | 1989-10-04 | 航空航天部三十一所 | Self-exciting catalytic igniter |
| EP2484880A1 (en) * | 2011-02-04 | 2012-08-08 | Siemens Aktiengesellschaft | Liquid fuel assist ignition system of a gas turbine and method to provide a fuel/air mixture to a gas turbine |
| CN103452704A (en) * | 2013-08-09 | 2013-12-18 | 蔡肃民 | Miniature turbojet midair windmill ignition device |
| CN103935524A (en) * | 2014-04-29 | 2014-07-23 | 南京航空航天大学 | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
-
2016
- 2016-07-29 CN CN201610607726.0A patent/CN106089445B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2045430U (en) * | 1988-11-15 | 1989-10-04 | 航空航天部三十一所 | Self-exciting catalytic igniter |
| EP2484880A1 (en) * | 2011-02-04 | 2012-08-08 | Siemens Aktiengesellschaft | Liquid fuel assist ignition system of a gas turbine and method to provide a fuel/air mixture to a gas turbine |
| CN103452704A (en) * | 2013-08-09 | 2013-12-18 | 蔡肃民 | Miniature turbojet midair windmill ignition device |
| CN103935524A (en) * | 2014-04-29 | 2014-07-23 | 南京航空航天大学 | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110714838A (en) * | 2019-11-01 | 2020-01-21 | 北京动力机械研究所 | Turbojet engine started by gas |
| CN114062816A (en) * | 2021-11-17 | 2022-02-18 | 四川航天长征装备制造有限公司 | Electric explosion valve test system and test method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106089445B (en) | 2018-05-04 |
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